Prior to the detailed design of components, turbomachinery engineers must guide a mean-line or throughflow design toward an optimum configuration. This process requires a combination of informed judgement and low-order correlations for the principle sources of loss. With these requirements in mind, this paper examines the impact of key design parameters on endwall loss in turbines, a problem which remains poorly understood. This paper presents a parametric study of linear cascades, which represent a simplified model of real-engine flow. The designs are nominally representative of the low-pressure turbine blades of an aero-engine, with varying flow angles, blade thickness, and suction surface lift styles. Reynolds-averaged Navier–Stokes (RANS) calculations are performed for a single aspect ratio (AR) and constant inlet boundary layer thickness. To characterize the cascades studied, the two-dimensional design space is examined before studying endwall losses in detail. It is demonstrated that endwall loss can be decomposed into two components: one due to the dissipation associated with the endwall boundary layer and another induced by the secondary flows. This secondary-flow-induced loss is found to scale with a measure of streamwise vorticity predicted by classical secondary flow theory.
Endwall Loss in Turbine Cascades
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received October 24, 2016; final manuscript received December 16, 2016; published online March 15, 2017. Editor: Kenneth Hall.
- Views Icon Views
- Share Icon Share
- Cite Icon Cite
- Search Site
Coull, J. D. (March 15, 2017). "Endwall Loss in Turbine Cascades." ASME. J. Turbomach. August 2017; 139(8): 081004. https://doi.org/10.1115/1.4035663
Download citation file:
- Ris (Zotero)
- Reference Manager